Low-Thrust Orbit Transfer

A typical in-orbit problem is a transfer from the geostationary transfer orbit (GTO) to the geostationary orbit (GEO). One possibility to do so is the use of a low-thrust electric propulsion system. In this case the transfer lasts up to several months but the fuel mass consumption is just a small part of what would be needed with chemical propulsion. During the low-thrust transfer the spacecraft is spiraling from the GTO to the final GEO in dozens or even hundreds of revolutions.

In fact, this makes the trajectory optimization problem a challenge with hundreds of thousands of optimizable parameters. A software that can handle this kind of problems is the sparse optimal control software SOCS from The Boeing Company.

In past years, analyses for missions like SMART-1, ConeXpress and SMART-OLEV were conducted from feasibility studies to operational purpose with increasing sophistication. Examples of low-thrust orbit transfer problems solved so far are:

Time-optimal transfer (minimum time)

Fuel-optimal transfer (for an additional amount of transfer time, e.g. +10% of the time-optimal solution)

Re-optimization of perturbed transfers following a reference trajectory

Monte-Carlo Analysis

Another in-orbit application is the analysis of the influence of gravity field uncertainties to operational orbits. Uncertainties of the gravity field model can not be neglected, especially in case of long-term missions in low altitude orbits like the German Moon mission LEO.

Feasibility of Proximity Operations at Small Asteroids

Possible close proximity operations at small asteroids are orbiting in a photo-gravitational orbit, hovering, flyovers and landings. Services we provide include general feasibility, delta-v and reference trajectories.